JP4092728B2 - Aircraft propulsion system - Google Patents

Description

  The present invention relates to an aircraft propulsion system, and more particularly to an aircraft propulsion system that can ensure an optimum thrust and thrust direction according to a flight state, an optimum engine cross-sectional area, and has high environmental compatibility.

For aircraft engines, there is an optimum thrust and thrust direction and engine cross-sectional area required for each flight condition including takeoff, cruise and landing.For example, maximum thrust is required at takeoff, or at landing. Although thrust is required in the direction of increasing the braking direction, it is required that the air resistance does not increase during cruising. A turbofan engine with a large bypass ratio, which is often used as a highly efficient civil engine, has a large air intake area (engine cross-sectional area) and does not require thrust as much as takeoff during high-speed cruising. The cross-sectional area increases the resistance of the fuselage and adversely affects flight performance. For the purpose of simply increasing the thrust, an afterburner may be installed at the rear of the core engine to reduce the fan's outer diameter. However, the operation of the afterburner causes significant noise and is also desirable for engine operating efficiency. I can not say. As described above, it is difficult for an ordinary fixed engine to achieve an optimal engine arrangement and engine cross-sectional area in all flight states. However, the advantage of deflecting the thrust direction of an aircraft engine is great in aircraft operation, and various concepts have been proposed and put into practical use. For example, Patent Document 1 discloses a turbofan engine having a variable thrust direction.
Among them, thrust deflecting nozzles that make the engine itself movable or deflect the nozzles have high utility value for military aircraft that require agile change of thrust direction vector in aircraft operation, but large aircraft There are not many advantages that apply to civilian aircraft, which account for the majority of The most common demand for commercial aircraft for thrust deflection is during takeoff and landing. At takeoff, exhaust from the engine mounted below the wing surface is created by a high lift device aimed at increasing lift by the Counder effect by lowering the flap at the rear end of the wing, creating lift by deflection of the engine itself in the vertical take-off and landing aircraft There is a method of obtaining upward lift by receiving air supply from an air source and directing the fan upward at takeoff. However, these tend to have limited effects or have complicated moving mechanisms. On the other hand, at the time of landing, it is already a general matter to reduce the braking distance at the time of landing by generating a reverse thrust by a reverse injection device. The reverse thrust generation mechanism also requires a slightly complicated mechanism.

  In addition, as a performance item required for an aircraft engine, environmental compatibility, that is, low noise and low harmful exhaust gas volume has recently been screaming loudly. Many aircraft engines use turbofan engines with a high bypass ratio in order to achieve high efficiency and low noise. However, aircraft engines that are improved year by year are limited in their development from the viewpoint of environmental compatibility, and proposals for new engine systems are essential if fundamental performance improvements are required. For example, as a direction required for a new engine system, from the standpoint of low noise, an increase in the bypass ratio due to further expansion of the fan diameter is required, and from the viewpoint of a low harmful exhaust gas volume, the electric output of the engine is required. It can be said that the times are indispensable. Incidentally, Patent Document 2 discloses a fuel cell type turbine engine in which a motor is driven by a fuel cell, a turbine is driven by the motor, and a fan is driven by a shaft output of the turbine.

Japanese Unexamined Patent Publication No. 2003-137192 (Invention name “Vertical take-off and landing aircraft”, published on May 14, 2003) Japanese Patent Laid-Open No. 11-137192 (Title of Invention “Fuel Cell Type Turbine Engine”, Published July 27, 1999)

The turbofan engine with a thrust deflection mechanism of Patent Document 1 has a problem that the mechanism is complicated and increases in weight.
In addition, a combination of a conventional electric motor and a turbofan engine, or the fuel cell turbine engine of Patent Document 2 described above has environmental compatibility but has limited output, and naturally has a limit to applicability to large aircraft. It can be said that there is.
An object of the present invention has been made in view of the above-mentioned problems of the prior art, and can ensure the optimum thrust and thrust direction and the optimum engine cross-sectional area according to the flight state and has high environmental compatibility. The object is to provide an aircraft propulsion system.

In order to achieve the above object, according to a first aspect of the present invention, there is provided an aircraft propulsion system including a first propulsion device that generates thrust and a second propulsion device having thrust deflecting means that makes the thrust direction variable. In the second propulsion device, the armature coil is disposed on the outer peripheral end of the fan, and the exciting coil is disposed on the inner peripheral surface of the casing of the fan facing the armature coil. And an electromagnetically driven fan driven by electromagnetic force generated by the mutual induction action of the exciting coils.
In the aircraft propulsion system according to the first aspect of the invention, the second propulsion device is an electromagnetically driven fan driven by electromagnetic force generated by the mutual induction action of the armature coil and the exciting coil, and does not use chemical fuel as an energy source. The total amount of exhaust gas containing harmful substances is suitably reduced. Further, since the armature coil is disposed at the outer peripheral end of the fan, a heavy object such as an iron core is not required, the weight is reduced, and a large torque can be obtained by the electromagnetic force generated by the mutual induction action. The outer diameter can be increased. Thereby, while a thrust increases, a bypass ratio can be raised and it becomes a low noise. Furthermore, the electromagnetic drive fan eliminates the need for the core engine and is simple in configuration, and the auxiliary device is mainly a power supply line, and a flexible one can be adopted as the line, so that the thrust direction can be changed. There is no hindrance. Thereby, environmental compatibility improves while ensuring the optimal thrust and thrust direction according to the flight state of the aircraft.

According to a second aspect of the invention, there is provided storage means for storing the second propulsion device inside the blade or closing it to the outer surface of the blade, and blade moving means for moving the second propulsion device in the blade width direction and the chord direction. It was decided.
In the aircraft propulsion system according to the second aspect of the invention, the second propulsion device can be stored in the wing during high-speed cruising. Therefore, the front projection area of the aircraft can be reduced, and the air resistance of the aircraft can be reduced. Further, since the second propulsion device can move in the blade width direction or the chord direction, the bypass ratio of the first propulsion device can be dramatically increased by arranging the second propulsion device coaxially with respect to the first propulsion device, for example. And the noise level during exhaust of the first propulsion device can be reduced. As a result, environmental compatibility is improved while ensuring an optimal engine cross-sectional area corresponding to the flight state of the aircraft.

In a third aspect of the invention, the first propulsion device or the second propulsion device includes an electric output generating means.
In the aircraft propulsion system according to the third aspect of the present invention, the electric power generated by the electric output generating means can be suitably supplied to the electromagnetically driven fan as the second propulsion device. As a result, the operating ratio of the electromagnetically driven fan can be increased, and as a result, the ratio of chemical fuel as a power source can be reduced and the ratio of electrical energy can be increased, so the total amount of exhaust gas containing harmful substances is reduced. To come.

In the fourth invention, the electric output generating means is a generator, a fuel cell, or a combination of them and a storage battery.
In the aircraft propulsion system of the fourth aspect of the invention, it is possible to store electricity while efficiently generating power by combining a fuel cell or a storage battery with them in addition to a normal generator. As a result, the ratio of chemical fuel as a power source decreases and the ratio of electrical energy can be increased, so that the total amount of exhaust gas containing harmful substances decreases.

In a fifth aspect of the invention, the fuel in the first propulsion device and the fuel cell is liquid hydrogen.
In the aircraft propulsion system according to the fifth aspect of the invention, since the fuel is liquid hydrogen, the combustion temperature is lowered by water vapor generated as a result of combustion with air, and as a result, the production of nitrogen oxides is suitably suppressed. In addition, since carbon is not contained in the fuel itself, emission of carbon compounds such as carbon dioxide can be suppressed, and environmental compatibility is dramatically improved.

According to a sixth aspect of the invention, the liquid hydrogen includes means for bringing the armature coil and the exciting coil into a superconducting state and receiving heat from the first propulsion device or the second propulsion device to vaporize the liquid hydrogen. did.
In the aircraft propulsion system according to the sixth aspect of the invention, the armature coil and the exciting coil are brought into a superconducting state by liquid hydrogen. Thereby, since the internal resistance of the coil is reduced as much as possible, almost no electric power is consumed when the electromagnetically driven fan as the second propulsion device is driven, and the energy efficiency is dramatically improved. Further, since the exhaust takes heat corresponding to the heat of vaporization of liquid hydrogen, the temperature of the exhaust decreases, and as a result, the generation of nitrogen oxides is suitably suppressed.

In a seventh aspect, the fuel cell is disposed between a compressor and a combustor constituting the first propulsion device.
In the aircraft propulsion system of the seventh aspect, compressed air can be supplied to the oxidant side electrode of the fuel cell, and vaporized hydrogen gas can be supplied to both the fuel cell and the combustor. This increases the power generation efficiency of the fuel cell and at the same time increases the combustion efficiency.

In an eighth aspect of the invention, the second propulsion device includes means for increasing the inlet pressure of the fuel cell.
In the aircraft propulsion system according to the eighth aspect of the invention, the power generation efficiency of the fuel cell is dramatically improved.

The aircraft propulsion system of the present invention has the following effects from the viewpoint of improving flight performance.
(1) Since the second propulsion device is an electromagnetically driven fan in which the armature coil is disposed on the outer peripheral end of the fan and the exciting coil is disposed on the inner peripheral surface of the casing of the fan, the core engine and the core iron A heavy object such as a core is not required, and the configuration is simplified and the weight is greatly reduced and the weight is reduced.
(2) As a result, thrust deflection means for changing the thrust direction, storage means for storing the second propulsion device inside the blade or closing the blade surface, blade movement for moving the second propulsion device in the blade width direction and the chord direction Means are easily realized. As a result, it is possible to secure the optimum thrust and thrust direction according to the flight state, and to secure the optimum engine cross-sectional area according to the flight state.
The aircraft propulsion system of the present invention has the following effects from the viewpoint of environmental compatibility.
(1) Since the second propulsion device is an electromagnetically driven fan and uses electric energy as an energy source, it does not exhaust exhaust gas containing harmful substances.
(2) Since the first propulsion device is equipped with electric output generating means, it suitably generates and stores electric energy to increase the operating rate of the electromagnetically driven fan, and as a result, the total amount of exhaust gas containing harmful substances is reduced. .
(3) Liquid hydrogen is used as the fuel, and since the liquid hydrogen brings the armature coil and the excitation coil of the electromagnetically driven fan into a superconducting state, there is almost no electrical resistance loss. As a result, the energy efficiency of the electromagnetically driven fan is increased. Further, since liquid hydrogen exchanges heat with the exhaust, the energy of the exhaust is recovered, and as a result, the energy efficiency of the entire system is improved.
(4) Further, the vaporized hydrogen gas is supplied to the fuel cell and the combustion chamber, and the power generation efficiency of the fuel cell is improved due to the fuel cell being disposed between the compressor and the combustor.
(5) Further, in the combustor, the temperature of the exhaust gas is lowered by water vapor generated as a result of the combustion reaction, and the generation of nitrogen oxides is suitably suppressed. At the same time, carbon dioxide is not emitted because the liquid fuel does not contain carbon compounds.
(6) In the electromagnetically driven fan, the armature coil that generates electromagnetic force is disposed at the outer peripheral end of the fan, so that a large torque can be generated, and as a result, the outer diameter of the fan can be increased. it can. This increases the bypass ratio and reduces the noise level during exhaust.

  Hereinafter, the present invention will be described in more detail with reference to embodiments shown in the drawings.

FIG. 1 is a configuration explanatory view showing an aircraft propulsion system 100 according to an embodiment of the present invention.
This aircraft propulsion system 100 deflects the thrust direction of turbofan engines 1 and 1 as first propulsion devices that generate thrust, electromagnetically driven fans 10 and 10 as second propulsion devices, and electromagnetically driven fans. Rotating mechanism portions 2 and 2 as thrust deflection means, slide mechanism portions 3 and 3 as blade moving means for moving the electromagnetically driven fan in the blade width direction and the chord direction, and the electromagnetically driven fan inside the blade or the blade Storage mechanisms 4 and 4 as storage means for storing on the outer surface, liquid fuel lines 5 and 5 for supplying liquid hydrogen to be supplied to the turbofan engine while cooling each coil of the electromagnetically driven fan, and a turbofan Generated from heat exchangers 6 and 6 for exchanging heat from the engine exhaust and liquid fuel, power generation units 7 and 7 as means for generating electric output of the turbofan engine, and fuel cell And is configured to power comprises a power storage unit 8, 8 power storage. Although the heat exchanger 6 and the power generation unit 7 are shown in parallel to the turbofan engine 1, they may be coaxial. The electromagnetically driven fan 10 will be described in detail with reference to FIGS.

The rotating mechanism unit 2 is configured by combining a rotating machine with a rotating shaft, for example. Incidentally, the rotating machine may be either electric or hydraulic.
The slide mechanism unit 3 is configured by combining a plurality of reciprocating machines, for example. Incidentally, the reciprocating machine may be either electric or hydraulic.
The storage mechanism unit 4 is configured, for example, by combining a rotary machine with a hinge. Incidentally, the rotating machine may be either electric or hydraulic.
In the liquid fuel line 5, liquid hydrogen as fuel flows, the armature coil and the exciting coil of the electromagnetically driven fan 10 are cooled to a superconducting state, and then heat energy is received from the exhaust of the turbofan 1 in the heat exchanger 6. Part of the fuel is vaporized in the combustor of the turbofan 1, and the rest is supplied to the fuel side electrode of the fuel cell 7. Although not shown, liquid hydrogen is stored in a cryogenic container, for example.
The heat exchanger 6 is, for example, one in which a thin tube is embedded in the exhaust nozzle of the turbofan 1.

  In the aircraft propulsion system 100, one electromagnetically driven fan 10 is arranged on each wing, but the electromagnetically driven fan 10 is also arranged on the front side of the turbofan engine 1. It is also possible to adopt a configuration in which two units are arranged on each wing.

  According to the aircraft propulsion system 100, since the electromagnetically driven fan is light in weight and simple in configuration, the thrust deflection mechanism, the storage mechanism, and the wing moving mechanism can be easily realized, and optimally suited to the flight state. The thrust, the thrust direction, and the engine cross-sectional area can be ensured.

FIG. 2 is a main part front view showing the electromagnetically driven fan 10 according to the embodiment.
This electromagnetically driven fan 10 increases the flow velocity of the intake air as it is and ejects it rearward, and a fan blade 11 that generates a thrust in the direction opposite to the ejection direction by the reaction, and a shaft to which the fan blade 11 is attached. 22, a fan casing 33 that houses the fan blade 11 and the shaft 22, and an effective electromagnetic force that is attached to the inner peripheral surface of the fan casing 33 so as to face the outer peripheral end of the fan blade 11 and rotates the fan blade 11. Divided excitation that generates an effective magnetic field and induces an effective induction current related to the effective electromagnetic force in the following divided armature coils, as well as a coil A _i row (i = 1, 2,..., N) as divided excitation coils. coil B _i row as coils (i = 1,2, ···, n ) and, the effective magnetic field is attached to the outer edge of the fan blade 11 and Serial coil M _i rows as divided armature coil generating the effective electromagnetic force by the interaction of the effective induced current (i = 1,2, ···, n ) and, of current to the coil A _i and the coil B _i a current control unit 44 for controlling is configured by including a position detection sensor for detecting an angle or displacement of the coil M _i (not shown). Incidentally, split excitation coils changes the role according to the relative position with respect to the coil M _i, i.e. the effective and an effective magnetic field of the electromagnetic force is supplied to the coil M _i and coil M _i when overlapping in the central portion of the coil M _i the effective induced current according to the effective electromagnetic force when overlapping one end induced in the coil M _i. Therefore, description for convenience, the coil B _i if induced coil A _i the case of forming the effective magnetic field according to the effective electromagnetic force in the coil M _i, or the effective induced current according to the effective electromagnetic force in the coil M _i However, the coils are completely the same in structure, and the divided excitation coil is also a coil A _i and a coil B _i .

Although not shown, the two liquid fuel lines 5, 5 on the in side and the out side are connected to the fan blade 11 and the fan casing 33, and the liquid hydrogen supplied from the liquid fuel supply line 5 on the in side. Circulates and cools the coil A _i row, the coil B _i row, and the coil M _i to a superconducting state. Thereafter, the liquid hydrogen is supplied to the heat exchanger 6 of the turbofan engine 1 while flowing through the liquid fuel supply line 5 on the out side to exchange heat with the exhaust gas, and the liquid fuel is vaporized and the fuel side electrode of the fuel cell 7 and turbo It is used for the combustor of the fan engine 1.

In the present embodiment, as shown in FIG. 3, when the width length of the coil M _i is L ₁ , the width length L ₂ of the coil A _i or the coil B _i is set to be substantially L _1/2 . .

  The effective magnetic field is a magnetic field that causes generation of the effective electromagnetic force in the magnetic field formed by the split excitation coil in the split armature coil. The effective induction current is the split excitation. This is the induced current that is the cause of the generation of the effective electromagnetic force among the induced currents that the coil induces in the split armature coil.

The current control device 44 relates to the current control of the coil A _i row and the coil B _i row. For example, the coil A _i , the coil B _i , and the coil A Control is performed with _{i + 1} and coil B _{i + 1} as a set.

According to the electromagnetically driven fan 10, the coil M _i rows as armature coils (i = 1,2, ···, n ) is disposed on the outer edge of the fan blade 11 need not iron core or the like Since the structure is adopted, the entire weight can be reduced. Further, the coil M _i rows (i = 1,2, ···, n ) because is disposed on the outer peripheral edge of the furthest fan blade 11 from the center of rotation, generating a large torque at a relatively small effective electromagnetic force Thus, the fan blade 11 can be suitably rotated.

FIG. 3 is an explanatory diagram showing a two-dimensional relative position of the coil A _i row or the coil B _i row with respect to the coil M _i row.
This figure shows a state in which projection of the coil M _i rows on the inner peripheral surface of the fan casing 33, the expansion of the inner peripheral surface of the fan casing 33 as a two-dimensional plane. Since the coil A _i row or coil B _i strings are disposed on the inner peripheral surface of the fan casing 33 stationary relative to the coil M _i rows, whereas, the coil M _i rows to the outer peripheral edge of the fan blade 11 Since it is disposed, it moves relative to the coil A _i row or the coil B _i row.

The coil A _i or the coil B _i is, for example, a rectangular and single-turn or double-turn divided excitation coil, and the capacitor C constituting the LC circuit together with the coil A _i or the coil B _i at the end, the coil A _i or the coil first and second thyristors SCR ₁ to conduct bidirectional current to B _i, and SCR _2, the power supply and the switching circuit SW for switching the bias direction of the capacitor C depending on the polarity of the capacitor C, the charge on the capacitor C S. Incidentally, the switching control of the first and second thyristor SCR _1, SCR ₂ of the switching control and switching circuit SW is performed by the current control device 44 based on information from the position detecting sensor indicating the rotational position of the coil M _i.

Regarding the operation of the electromagnetically driven fan 10, the coil A _i and the coil B _i are common in that they contribute to generation of an effective electromagnetic force that rotates the fan blade 11 with respect to the coil M _i . _In the mechanism by which _i generates its effective electromagnetic force, the roles of coil A _i and coil B _i are completely different. That is, the coil A _i gives an effective magnetic field related to the effective electromagnetic force to the coil M _i , while the coil B _i plays a role of inducing an effective induction current related to the effective electromagnetic force in the coil M _i . Then, the invalid induced current coil A _i does not contribute to the rotation of the fan blades 11 that induced in the coil M _i, fan blades coil B _i is on the coil M _i with the suitably counteracted by the features of the structure of the coil M _i The ineffective electromagnetic force due to the ineffective magnetic field that does not contribute to the rotation of 11 is also canceled out.

Furthermore, since the coil A _i or the coil B _i constitutes an LC circuit together with the capacitor C, the current flowing through the coil A _i or the coil B _i when the thyristor is turned on is a time-variable current, so-called alternating current. Current. Thus, when flowing through the coil A _i or coil B _i the alternating current as the exciting current, that since the fluctuating magnetic field the time passing through the coil M _i is formed by the excitation current, the coil M _i by the time variation of the magnetic field An induced current flows in a direction that prevents temporal fluctuation of the magnetic field. Thus, current can flow in the coil M _i as armature coils without supplying a current from the outside.

Further, if the current flowing through the coil A _{i + 1} is I _{ai + 1} and the current flowing through the coil B _{i + 1} is I _{bi + 1} , the adjacent coils A or the coils B are equal in size and opposite in direction. That is, | I _ai | = | I _{ai + 1} | and I _ai = −I _{ai + 1} or | I _bi | = | I _{bi + 1} | and I _bi = −I _{bi + 1} .

In general, when the width dimension of the coil _{A i} or coil _{B i} to the width length of _{L 2} and the coil _{M i} and _{L 1,} between the _{L 1} and _{L 2} the relationship between the _L 1/2 ≦ _L 2 _{<L 1} Is true. Thereby, the magnetic field generated by energizing the coil A _i or the coil B _i can be efficiently applied to the coil M _i . In this embodiment, L ₂ = L _1/2 .

The coil M _i is an eight-shaped coil that intersects at the center and has a symmetrical shape. For convenience of illustration, the coil M _i is a single winding, but may be a multiple winding. As a result of this crossing, for example, the induced currents induced by the coil A _i in the coil M _i cancel each other out in the center, and as a result, the coil A _{i only} receives the effective magnetic field related to the effective electromagnetic force that contributes to the rotation of the fan blade 11. It will be given to the coil _{M i.} On the other hand, for example, the induced current coil B _i and coil B _{i + 1} is induced in the coil M _i flows in mutually the same direction at the central portion, the electromagnetic force generated by the induced current but is added, the coil M _i At both ends, the directions of the magnetic fields formed by the coil _Bi and the coil _{Bi + 1} in the coil Mi _{+ 1} are opposite to each other, and the induced currents flow in the same direction, and are generated by the interaction between the magnetic field and the induced current. The electromagnetic forces cancel each other, and as a result, the coil B _i and the coil B _{i + 1} induce only the effective induction current related to the effective electromagnetic force in the coil M _i . An effective electromagnetic force is generated by the interaction with the effective induction current and the effective magnetic field, and the fan blade 11 is rotated by the effective electromagnetic force.

  In this embodiment, a thyristor is employed as the switching means, but a semiconductor switching element such as a power transistor, a power MOSFET, or an IGBT may be used.

  The power source S is, for example, a secondary battery, and electric power is supplied from a generator and a fuel cell as a power generation unit 7 to be described later, a fuel cell and a storage battery, a single fuel cell, a single storage battery, or a combination thereof. The

In the electromagnetically driven fan 10, the electric energy supplied to excite the divided excitation coils such as the coil B _i and the coil B _{i + 1} is suitably recovered and stored as electric energy again by the capacitor C, and is switched by switching means such as a thyristor. It is reused to excite the split excitation coil again. Thus, the electromagnetically driven fan 10 has an energy recovery function. Furthermore, since the split armature coil and the split excitation coil are brought into a superconducting state by liquid hydrogen as described later, they have extremely low resistance. Therefore, in the process of generating an effective electromagnetic force that rotates the fan blade 11, little electric energy is used to excite the split excitation coil, and the energy efficiency of the electromagnetically driven fan is extremely high.

FIG. 4 is an explanatory diagram showing an application example of the aircraft propulsion system 100 of the present invention to an aircraft.
In the aircraft propulsion system 100 shown in this application example, one turbofan engine 1 as a first propulsion device and one electromagnetically driven fan 10 as a second propulsion device are arranged on each wing of an aircraft.

  First, in FIG. 4A, for example, in the initial takeoff state where the aircraft shifts from a stationary state to an acceleration state, the electromagnetically driven fan 10 is operated by the rotating mechanism unit 2 as the thrust deflecting unit so that the thrust in the horizontal direction is maximized. The thrust direction of the is consistent with the direction of travel. Next, in FIG. 4B, for example, in the final takeoff state where the aircraft takes off by receiving lift, the rotation angle is inclined backward by the rotation mechanism unit 2 as the thrust deflector so that the thrust in the takeoff direction increases. By doing so, the thrust direction of the electromagnetically driven fan 10 coincides with the takeoff direction. Next, in FIG. 4C, for example, in a cruising state in which an aircraft is constantly sailing at a predetermined altitude and speed, the electromagnetically driven fan 10 is operated by the slide mechanism 3 as the wing moving means in order to reduce the air resistance as much as possible. Arranged forward and coaxially with respect to the turbofan engine 1, the front projected area of the aircraft is reduced, and the air resistance of the aircraft during cruising is reduced. Alternatively, the electromagnetically driven fan 10 is stored inside the wing by the storage mechanism unit 4 as a storage means. As a result, the front projection area of the aircraft is reduced, and the air resistance of the aircraft during cruising is reduced. Next, in (d) of FIG. 4, for example, when the aircraft is in a landing state, the turbofan engine 1 reversely injects its own fan so that thrust reverse to the traveling direction is generated, while the electromagnetically driven fan 10 is excited. The direction of travel by rotating the fan blade 11 in the reverse direction with the direction of the current flowing in the coil reversed or by rotating the fan blade 11 forward by changing the rotation phase angle of the electromagnetically driven fan 10 by 180 degrees by the rotation mechanism 2. The thrust in the opposite direction is generated.

  As described above, since the electromagnetically driven fan 10 is light in weight and simple in configuration, a thrust deflection mechanism, a wing moving mechanism, and a storage mechanism can be easily added to the electromagnetically driven fan 10, and the aircraft The propulsion system 100 can ensure the optimum thrust, thrust direction, and engine cross-sectional area according to the flight state. In particular, it is possible to realize high lift by thrust deflection at takeoff, reduction of air resistance by fan folding at cruise, and generation of reverse thrust at landing. That is, short takeoff and landing and low resistance cruise can be easily realized.

FIG. 5 is an explanatory diagram showing the power generation unit 7 as an electrical output generating means of the aircraft propulsion system according to the present invention.
First, in FIG. 5A, a generator 71 is connected to the fan drive shaft 15 of the turbofan 1, and the generator is rotated by the shaft output of the low-pressure turbine 14 to generate electric power. The generated electric power is supplied to a power storage unit 8 (not shown), for example, an electromagnetically driven fan and other electric machines and electronic devices while being stored by a storage battery. Next, in FIG. 5B, a generator 71 is connected to the fan drive shaft 15 of the turbo fan 1 as an electric output generating means, and the generator 71 is rotationally driven by the shaft output of the low-pressure turbine 14 to generate electric power. At the same time, electric power is generated by the fuel cell 72 using air from the compressor 12 as an oxidant and liquid hydrogen as a fuel. The fuel cell 72 is disposed between the compressor 12 and the combustor 13 of the turbofan 1. Thereby, compressed air can be supplied to the oxidant side electrode of the fuel cell 72, and the power generation efficiency of the fuel cell 72 is improved. Alternatively, the fuel cell 72 may be provided in parallel with the turbofan engine 1 so that the compressed air is diverted from the compressor outlet and introduced into the oxidant side electrode of the fuel cell 72. Next, FIG. 5C shows a combination of a fuel cell 72 and a storage battery (not shown) that use air from the compressor 12 as an oxidant and liquid hydrogen as a fuel as electrical output generating means. Like FIG. 5B, the fuel cell 72 is disposed between the compressor 12 and the combustor 13 of the turbofan 1, or the fuel cell 72 is provided in parallel with the turbofan engine 1 and compressed air. Is split from the compressor outlet and introduced into the oxidant side electrode of the fuel cell 72. The storage battery is a so-called secondary battery.

  Liquid hydrogen is used as the fuel for the fuel cell, but the liquid hydrogen is not introduced into the fuel-side electrode of the fuel cell in the liquid state. First, the liquid hydrogen is an armature coil and an excitation coil of the electromagnetically driven fan 10. Is cooled to a superconducting state. As a result, a current can be passed through the armature coil and the exciting coil with almost no electric resistance loss, and the energy efficiency of the electromagnetically driven fan 10 is improved. Thereafter, the liquid hydrogen is introduced into a heat exchanger 6 provided inside the exhaust nozzle. As a result, the energy of the exhaust is recovered as thermal energy, and the energy efficiency of the entire system is improved. The liquid hydrogen is vaporized by the heat exchanger 6 and then supplied to the combustor 13 of the turbofan engine 1 and the fuel side electrode of the fuel cell 72, respectively. Hydrogen burns and reacts with compressed air in the combustor to produce water vapor. This water vapor lowers the combustion temperature and suitably suppresses the generation of nitrogen oxides, so-called NOx. Moreover, since hydrogen fuel does not contain carbon, it does not emit carbon dioxide, which causes global warming. Furthermore, since the electric power generated by the electric output generating means such as a generator or a fuel cell becomes a driving source for the electromagnetically driven fan 10, the operating rate of the turbofan engine 1 including the combustor is reduced to operate the electromagnetically driven fan 10. By increasing the rate, the total exhaust containing nitrogen oxides is reduced. Accordingly, the environmental compatibility is dramatically improved as compared with the conventional aircraft propulsion system using fossil fuel.

  On the other hand, in the electromagnetically driven fan 10, since the armature coil is disposed at the outer peripheral edge of the fan, a large torque can be generated and the outer diameter of the fan blade 11 can be increased. As a result, the electromagnetically driven fan 10 is disposed in front of the shaft of the turbofan engine 1 by the slide mechanism unit 3, the bypass ratio of the turbofan engine 1 is increased, and the noise level is reduced.

  Although the effectiveness of gas turbines and fuel cells using hydrogen as fuel has already been studied and known, the biggest drawback was the volume and weight involved in hydrogen storage. Although there is a point that a solution is awaited for further research on materials and the like, if the liquid hydrogen can be effectively used in the entire engine system, the drawback is more than compensated. An electromagnetically driven fan can ensure extremely high efficiency and performance by using a superconducting coil. Although its effectiveness has been shown in the test operation of magnetic levitation railways, the superconducting state is mainly secured by liquid helium at a large practical test level. Cryogenic temperatures reaching Kelvin. From this fact, superconducting technology is difficult from the viewpoint of cryogenic environment utilization, and research is being conducted with the goal of securing a superconducting state at a higher temperature to eliminate the difficulty. One temperature target is one that is compatible with 77 Kelvin, the boiling point of liquid nitrogen. Several things corresponding to this temperature have been realized in the research stage, but they have not yet reached the practical stage. However, the liquid hydrogen described in this example has a boiling point of 14 Kelvin, and a relatively large number of materials corresponding to this temperature have been studied, and its practical potential is high compared to liquid nitrogen. Liquid hydrogen is gasified by using regenerative heat exchange with engine exhaust heat using liquid hydrogen as a superconducting drive medium. The gasified hydrogen is used as a fuel for a gas turbine or a fuel cell. Some fuel cells using hydrogen operate at a low temperature, but when used as a combined cycle with a gas turbine, a high-temperature operating fuel cell is used, and thermal efficiency is achieved through effective use of heat with the gas turbine. It is also possible to improve.

FIG. 6 is an exemplary diagram showing the operation of the pressure increasing means at the air inlet of the fuel cell.
When the fuel cell is used alone, the fan bypass ratio can be maximized among the examples of the core engine excluding the storage battery, which is desirable for environmental compatibility. In the case of using a fuel cell, the pressure of air supplied to the fuel cell can be easily increased by combining with a gas turbine such as the turbofan engine 1. It is necessary to increase the pressure of the battery intake air compared to the exhaust of most fans. An example of the pressure increasing means for this purpose is shown in FIG. As shown in FIG. 6 (a), a small boost fan 20 is provided in the wake that is coaxial with the electromagnetically driven fan 10 to increase the pressure of the fuel cell air inlet. As shown in FIG. 6 (b), by appropriately designing the blade cascade of the fan, the pressure increase at the outer peripheral portion where the peripheral speed is large is made larger than that at the inner periphery, and the fuel cell air intake port is provided downstream. It is provided. In the example of FIG. 6B, the fuel cell is arranged on the outer periphery of the fan for ease of blade row design, but a deflection duct is provided on the inner side with respect to the fan rotation center axis. Is also possible. In either form, the fuel cell exhausts hot exhaust. This exhaust can contribute to the thrust by appropriately mixing with the fan exhaust air.

The aircraft propulsion system 100 according to the embodiment has the following effects from the viewpoint of improving flight performance.
(1) The electromagnetically driven fan 10 is an electromagnetically driven fan in which the armature coil is disposed at the outer peripheral end of the fan blade 11 and the exciting coil is disposed on the inner peripheral surface of the fan casing. A heavy object such as a core iron core is not required, and the configuration is simplified and the weight is greatly reduced and the weight is reduced.
(2) As a result, a thrust deflection mechanism that changes the thrust direction, a storage mechanism that houses or closes the second propulsion device inside the blade, and blade movement that moves the second propulsion device in the blade width direction and the chord direction The mechanism is easily realized. As a result, it is possible to secure the optimum thrust and thrust direction according to the flight state, and to secure the optimum engine cross-sectional area according to the flight state.
In addition, the aircraft propulsion system 100 of the present invention has the following effects from the viewpoint of environmental compatibility.
(1) Since the electromagnetic drive fan 10 uses electric energy as an energy source, the electromagnetic drive fan 10 does not discharge exhaust gas containing harmful substances.
(2) Since the turbofan engine 1 is equipped with electrical output generating means, it suitably generates and stores electrical energy to increase the operating rate of the electromagnetically driven fan 10, thereby reducing the total amount of exhaust gas containing harmful substances. To do.
(3) The electromagnetically driven fan 10 has an energy recovery function, and liquid hydrogen is used as a fuel for the turbofan engine 1, and the liquid hydrogen makes the armature coil and the exciting coil of the electromagnetically driven fan 10 superconductive. There is almost no electrical resistance loss. As a result, the energy efficiency of the electromagnetically driven fan is increased. Further, since liquid hydrogen exchanges heat with the exhaust, the energy of the exhaust is recovered as heat, and as a result, the energy efficiency of the entire system is improved.
(4) Further, the vaporized hydrogen gas is supplied to the fuel cell and the combustion chamber, and the power generation efficiency of the fuel cell is improved due to the fuel cell being disposed between the compressor and the combustor.
(5) Further, in the combustor, the temperature of the exhaust gas is lowered by water vapor generated as a result of the combustion reaction, and the generation of nitrogen oxides is suitably suppressed. At the same time, carbon dioxide is not emitted because the liquid fuel does not contain carbon compounds.
(6) In the electromagnetically driven fan 10, since the armature coil that generates electromagnetic force is arranged at the outer peripheral end of the fan, a large torque can be generated, and as a result, the outer diameter of the fan is increased. Can do. This increases the bypass ratio and reduces the noise level during exhaust.

  The aircraft propulsion system of the present invention can be suitably applied to an engine unit of an aircraft, particularly an engine unit of a large aircraft.

1 is a configuration explanatory view showing an aircraft propulsion system according to an embodiment of the present invention. It is a principal part front view which shows the electromagnetically driven fan concerning an Example. It is explanatory drawing which shows the two-dimensional relative position with respect to coil M _i row _| line _| column of coil A _i row _| line _| column or coil B _i row _| line _| column. It is explanatory drawing which shows the example of application with respect to the aircraft of the aircraft propulsion system of the present invention. It is explanatory drawing which shows the electric power generation part 7 as an electrical output generation means of the aircraft propulsion system which concerns on this invention. It is an illustration figure which shows operation | movement of the pressure increase means of the air inlet of a fuel cell.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Turbofan engine 2 Rotation mechanism part 3 Slide mechanism part 4 Storage mechanism part 5 Liquid fuel line 6 Heat exchanger 7 Fuel cell 8 Storage battery 11 Fan blade 22 Shaft 33 Fan casing 44 Current control apparatus A _i division excitation coil B _i division excitation Coil M _i- divided armature coil 10 Electromagnetic drive fan

Claims (8)

An aircraft propulsion system comprising a first propulsion device for generating thrust and a second propulsion device having thrust deflecting means for changing the thrust direction, wherein the second propulsion device intersects at a central portion and coil array of divided armature coil consisting of 8-shaped closed coil is symmetrical form (coil M _i rows (i = 1,2, ···)) from the and rectangular coil disposed in the outer peripheral end portion of the fan The coil array of the divided excitation coils (coil A _i array and coil B _i array (i = 1, 2,...)) Is divided into one divided armature coil (coil M _i ). Two split excitation coils (especially in the coil array of the split excitation coils) adjacent to the split excitation coil (especially referred to as “coil A” in the coil array of the split excitation coils) when overlapping the central portion. Is called “Coil B”. In this case, “Coil B _i-1 ” and “ And yl B _i ".) Is disposed on the inner peripheral surface of the casing portion of the fan so as to overlap at both ends of the divided armature coil (coil M _i),
In addition, each of the divided excitation coils has a capacitor (C) constituting an LC circuit, switching means for conducting a bidirectional current to each divided excitation coil, and a switching circuit (SW) for switching the bias direction of the capacitor (C). And a power source (S) for supplying electric charge to the capacitor (C),
In addition, at the timing when one divided exciting coil overlaps the central portion of one divided armature coil, the other two divided exciting coils that overlap both ends of the divided armature coil are supplied with alternating currents that are equal in size and opposite to each other. The divided armature coil is energized to induce an effective induction current that contributes to the rotation of the fan, while an alternating current is also passed to the divided excitation coil that overlaps the center of the divided armature coil. An electromagnetically driven fan that forms an effective magnetic field that contributes to the rotation of the fan that penetrates the center of the fan and drives the fan by the sum of effective electromagnetic forces generated by the interaction between the effective induced current and the effective magnetic field An aircraft propulsion system characterized by   2. The storage means for storing the second propulsion device inside the blade or closing it to the outer surface of the blade, and blade moving means for moving the second propulsion device in the blade width direction and the chord direction. The aircraft propulsion system described.   The aircraft propulsion system according to claim 1 or 2, wherein the first propulsion device or the second propulsion device includes an electric output generating means.   4. The aircraft propulsion system according to claim 3, wherein the electric output generating means is a generator, a fuel cell, or a combination of these and a storage battery. The aircraft propulsion system according to claim 4 , wherein the first propulsion device and the fuel cell have liquid hydrogen as a fuel.   6. The aircraft hydrogen according to claim 5, wherein the liquid hydrogen is provided with means for vaporizing the armature coil and the exciting coil by receiving heat from the first propulsion device or the second propulsion device while making the armature coil and the excitation coil in a superconducting state. Propulsion system. The aircraft propulsion system according to any one of claims 4 to 6 , wherein the fuel cell is disposed between a compressor and a combustor constituting the first propulsion device.   The aircraft propulsion system according to any one of claims 4 to 7, wherein the second propulsion device includes means for increasing an inlet pressure of the fuel cell.

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